Manufacturing method of partially cured composite components

Patent metadata

Field	Value
Publication number	US-9776386-B2
Application number	US-201414570009-A
Country	US
Kind code	B2
Filing date	Dec 15, 2014
Priority date	Dec 13, 2013
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

An efficient method for manufacturing a partially cured composite component intended to be joined with other component or components to form a composite structure and a manufacturing method of the composite structure. The partial curing of a composite layup is achieved using a mold comprising heat conductive elements and insulating elements and applying heat and pressure over the mold. The heat conductive elements are used to transmit or dissipate heat to/from the composite layup. The insulating elements are used to prevent the transmission or dissipation of heat to/from the composite layup.

First claim

The invention claimed is:

1. A method of manufacturing a partially cured composite component, the method comprising:
placing a composite layup inside a mold, the composite layup having a first side opposite a second side;
providing a source of pressure configured to apply pressure in a direction towards the first side of the composite layup;
providing a source of pressure configured to apply pressure in a direction towards the second side of the composite layup;
applying heat and pressure to the mold;
wherein the mold comprises a plurality of heat conductive elements and a plurality of insulating elements;

placing the heat conductive elements between the source of pressure configured to apply pressure in a direction towards the first side of the composite layup and the first side of the composite layup to transmit heat to those portions of the composite layup that shall be fully cured; and
placing the insulating elements between the source of pressure configured to apply pressure in a direction towards the first side of the composite layup and the source of pressure configured to apply pressure in a direction towards the second side of the composite layup to prevent the transmission of heat to those portions of the composite layup that shall remain un-cured and to prevent the dissipation of heat from those portions of the composite layup that shall be fully cured.

2. A method according to claim 1 , wherein the heat conductive elements and the insulating elements comprise rigid elements.

3. A method according to claim 2 , wherein the pressure is applied over two opposing faces of the mold.

4. A method according to claim 3 , wherein heat is applied over one of the faces of the mold where pressure is applied.

5. A method according to claim 2 , wherein the pressure is applied over two opposing faces of the mold and the heat is applied directly from heat conductive elements of the mold provided with heating elements.

6. A method according to claim 2 , wherein the heat conductive elements comprise steel boxes and the heat insulating elements comprise mica plates.

7. A method of manufacturing a composite structure, comprising:
preparing a first composite layup and one or more second composite layups;
curing partially said one or more second composite layups according to the method of claim 1 leaving un-cured those portions intended to be joined to the first composite layup;
assembling said first and second composite layups bringing in contact the un-cured portions of the one or more second composite layups with the first composite layup; and
co-curing the assembled set of said layups.

8. A method of manufacturing a composite structure according to claim 7 , wherein:
the composite structure comprises a reinforced skin of an aircraft lifting surface, the first composite layup is the skin layup and the second composite layups are T-shaped or omega-shaped stringers layups;
the un-cured portions of the stringer layups intended to be joined to the skin layup comprise feet and a contiguous portion of webs of the stringer layups;
a portion of the stringer layups farthest from the skin layup is cured;
an intermediate web portion of the stringer layups is partially cured.

9. A method according to claim 1 , wherein at least one heat insulating element is separated from at least one heat conductive element by the composite layup, the at least one heat insulating element positioned opposite the at least one heat conductive element.

Assignees

• Airbus Operations Sas
• Airbus Operations Sl
• Airbus Sas
• Airbus Operations Sas
• Airbus Sas

Inventors

• Garcia Solares Victor
• Munoz Lopez Pilar
• Zuarzo Ruiz Mar
• Fantina Llorente Betty
• Collart Cyrille
• Duprieu Bernard

Classifications

• B32B37/18 Primary

  involving the assembly of discrete sheets or panels only · CPC title

• B29C35/0266

  Local curing (for repairing B29C73/34) · CPC title

• B29C65/02

  by heating, with or without pressure · CPC title

• B29C66/131

  Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area · CPC title

• B32B38/1808

  characterised by the laying up of the layers · CPC title